Stationary ring assembly for a gas turbine

Abstract

A stationary ring assembly forming a rotor shroud for a gas turbine including a plurality of segments having adjacent side faces that are placed end to end with sealing means interposed therebetween. The sealing means include at least one axial sealing strip and at least one radial sealing strip respectively received in axial slots and in radial slots formed facing one another in the adjacent side faces of the segments. At least one end of each radial slot opens out into the corresponding axial slot, each axial slot of a segment presents a depth that is greater than the depth of the corresponding radial slot, and the axial sealing strip presents a width that is greater than the width of the radial strip.

1. A stationary ring assembly forming a rotor shroud for a gas turbine, the stationary ring assembly comprising:
 a plurality of segments having adjacent side faces that are placed end to end with sealing means interposed therebetween, the sealing means including at least one axial sealing strip and at least one radial sealing strip respectively received in axial slots and in radial slots formed facing one another in the adjacent side faces of the segments, at least one end of each radial slot opening out into the corresponding axial slot, wherein each axial slot of a segment presents a depth that is greater than the depth of the corresponding radial slot, the axial sealing strip presents a width that is greater than the width of the radial strip, and each radial slot does not extend beyond the corresponding axial slot. 
 
   
   
     2. The assembly according to  claim 1 , constituting a high-pressure turbine ring for a turbomachine. 
   
   
     3. The assembly according to  claim 2 , wherein each ring segment includes, in each side face, two axial slots disposed towards its inner and its outer walls, and in which axial strips are received, and two radial slots disposed towards its upstream and its downstream walls, and in which radial strips are received. 
   
   
     4. The assembly according to  claim 1 , constituting a high-pressure turbine spacer for a turbomachine. 
   
   
     5. The assembly according to  claim 4 , wherein each spacer segment includes, in each side face, one axial slot in which an axial strip is received, and at least three radial slots, two of which are disposed towards its upstream and its downstream walls, and in which radial strips are received. 
   
   
     6. A turbine including the assembly of  claim 1 . 
   
   
     7. A turbomachine including the assembly of  claim 1 . 
   
   
     8. A segment for a gas-turbine stationary ring assembly comprising:
 side faces configured to be placed end to end with sealing means interposed therebetween, the side faces including axial slots and radial slots configured to receive sealing means including at least one axial sealing strip and at least one radial sealing strip, respectively, at least one end of each radial slot opening out into the corresponding axial slot, wherein each axial slot of a segment presents a depth that is greater than the depth of the corresponding radial slot, and each radial slot does not extend beyond the corresponding axial slot.